Abstract: System for friction stir welding of two parts which includes a welding unit which includes at least one welding head fitted with a rotating pin and a counter-bearing unit which has a support surface to support the parts against a pressure exerted by the welding head, and wherein each welding head can be moved relative to the support surface in a first direction parallel to an axis of rotation of the rotating pin and in a second direction orthogonal to the axis of rotation, and wherein the support surface can be moved in the second direction and is formed of two coaxial clamp rollers which are set apart from each other.

Abstract: Simplification of the manufacture of composite material fuselages for aircraft, as well as mass reduction of fuselage sections and space optimization inside such fuselage sections. To accomplish this, it is proposed to use stringers of a new type which have a closed transverse section, and which are thus able to be self-positioned relative to one another by being positioned edge-to-edge on a stringer supporting structure, such as the outer surface of a mandrel. The installation of the stringers in grooves of conjugate shape is by this means made unnecessary. The stringers have cut-outs located between circumferential frames, and are able to house utility systems.

Abstract: A fuselage element including a fuselage segment including a skin and a junction means for connecting the skin to an adjacent fuselage segment. The fuselage segment extends along a longitudinal axis of the fuselage, and the skin includes a first section at at least one end of the fuselage segment. The fuselage segment includes at least one longitudinal stiffening element for the fuselage. A junction member is arranged so as to contact an outer surface of the first section of the skin, and the stiffening element partially extends to the junction member along the longitudinal axis.

Abstract: A rudder bar for an aircraft comprising a floor, a steering connecting rod and a braking connecting rod. The rudder bar comprises a base fixed above the floor, a pedal arm mounted rotatably on the base about a first axis of rotation and having a lower end and an upper end, a pedal mounted rotatably on the lower end about a second axis of rotation, a first transmission assembly configured to transmit a movement to the steering connecting rod when the pedal arm pivots about the first axis of rotation, and a second transmission assembly configured to transmit a movement to the braking connecting rod when the pedal pivots about the second axis of rotation.

Abstract: A support plate for the passage of systems between two zones at different pressurizations of an aircraft, in the region of a bulkhead separating the two zones. The support plate comprises a connection plate including at least one retaining element and at least one sealing joint and is provided with a plurality of holes intended for the passage of an assembly of systems which have to pass through said bulkhead.

Abstract: In order to limit the number of openings in an aircraft fuselage and to reduce the mass thereof, the invention makes provision for an item of aircraft fuselage equipment which is intended to be mounted in an opening of the fuselage, the item of equipment being configured to block/release an access passage which affords access to the inner side of the aircraft and which also comprises a discharge control valve for pressurization air.

Abstract: This stiffener is intended for a fuselage. It comprises a hollow section that can be trapezoidal, with a base attached to the fuselage or to the floor, high enough rising sides and a top side contributing to the rigidity and cohesion of the stiffener. A direct assembly with the fuselage is possible. The base is made of two edges provided one on the other or in front of the other. This rigid stiffener, in spite of its discontinuous section, can be manufactured by simple foldings of a planar metal sheet at the beginning.

Abstract: An intermediate support structure for the cockpit of an aircraft is provided. The intermediate support structure includes a raised floor and at least one structural element extending as an arch above the raised floor, the arched structure being adapted to hold in position at least one item of equipment in the upper part of the cockpit. The intermediate support structure also includes a fastener for mounting the intermediate support structure onto a fuselage primary structure, where the fuselage primary structure defines a portion of the cockpit of the aircraft.

Abstract: A door frame is provided at an opening made in a fuselage of an aircraft that is delimited by a skin. The frame includes an upper longitudinal stiffener and a lower longitudinal stiffener and two vertical substructures, each arranged on one side of the opening, connected by the upper and lower longitudinal stiffeners. The frame also comprises at least one stop provided at the level of the opening that uptakes radial forces exerted by the door. Each vertical substructure comprises at least three walls made of composite material that are connected to one another to form a box substructure having a closed and hollow cross-section in a sectional plane perpendicular to an axis of the length of the vertical substructure.

Abstract: In a fuselage portion for an aircraft, in order to reduce the assembly clearance between the soleplate of a circumferential frame and a fuselage skin in composite material while limiting the mass of the fuselage portion, a ply drop-off is used comprising two portions oriented in the circumferential direction and having different respective slopes.

Abstract: An aircraft including: at least one floor cross-member; at least one support carrying the cross-member; and at least one bearing including at least one flexible material and connecting the cross-member to the support.

Abstract: An aircraft nose structure includes a fuselage, a floor for a pressurized space and a nose landing gear bay arranged under the floor, on the opposite side to the space. The bay includes walls that form a pressure barrier, of which there are two lateral panels mechanically secured to the floor by load-reacting members, an upper panel adjacent to the floor and extending between the lateral panels, and a rear panel extending between the upper panel and the fuselage.

Abstract: An aircraft nose structure includes a fuselage and a pressuretight bulkhead fixed at its periphery to the fuselage and transversely dividing the fuselage into a pressurized upper zone and an unpressurized lower zone for accommodating retractable nose landing gear. The pressuretight bulkhead includes a floor of the pressurized upper zone, and a substantially flat rear panel extending between a rear edge of the floor and the fuselage. The floor and the rear panel are fixed laterally to the fuselage. The fuselage includes an exterior wall and reinforcing transverse frames to which the exterior wall is fixed. In line with the pressuretight bulkhead, at least some of the transverse reinforcing frames extend along the outline of the pressurized upper zone and constitute members that reinforce the pressuretight bulkhead.

Abstract: An aircraft floor portion includes crossmembers. Each crossmember comprises a top partial crossmember and a bottom crossmember, with at least one gap being left between the top partial crossmember and the bottom partial crossmember of each crossmember.

Abstract: A support plate for the passage of systems between two zones at different pressurizations of an aircraft, in the region of a bulkhead separating the two zones. The support plate comprises a connection plate including at least one retaining element and at least one sealing joint and is provided with a plurality of holes intended for the passage of an assembly of systems which have to pass through said bulkhead.

Abstract: An aircraft fuselage frame assembly includes a first lower frame element having a cross member and a curved fuselage tub frame. A second upper frame element of the assembly has a cross member and a curved upper frame segment. A third frame element of the assembly is made of a cross member section, floor strut section and frame section. The third frame element is formed as a single, integral triangle element having a hypotenuse that is curved to adopt a curvature of the aircraft fuselage and joining portions at angle areas of the triangle. A lower frame link is joined to the first upper frame and at a first angle area of the triangle element; an upper frame link is joined to the second upper frame and at a second angle area of the triangle element; and a floor cross member is joined at a third angle area of the triangle element.

Abstract: The sealed bottoms of aircraft passenger cabin have to be fastened with heavily sized fasteners so as to withstand loads induced by the cabin pressurization. Besides, the increase in aircrafts seating capacity makes an increase in passenger cabin widths of interest. Such a width increase however makes the structure delimiting passenger cabin less resistant to efforts induced by the cabin pressurization. The present invention proposes an aircraft wherein the structure delimiting passenger cabin extends over 360 degrees around a space defined outside structure. The invention allows structure to be more resistant to loads induced by the cabin pressurization, while allowing to reduce or even to avoid the need for a sealed bottom, and while allowing to increase the space available for passengers.

Abstract: Simplification of the manufacture of composite material fuselages for aircraft, as well as mass reduction of fuselage sections and space optimization inside such fuselage sections. To accomplish this, it is proposed to use stringers of a new type which have a closed transverse section, and which are thus able to be self-positioned relative to one another by being positioned edge-to-edge on a stringer supporting structure, such as the outer surface of a mandrel. The installation of the stringers in grooves of conjugate shape is by this means made unnecessary. The stringers have cut-outs located between circumferential frames, and are able to house utility systems.

Abstract: An aircraft of which the transversal section of the fuselage is reduced optimally at the price of a reduced carrying capacity of luggage or merchandise but adapted to short- and medium-haul type routes. The fuselage has for this purpose lateral protuberances defining storage areas arranged on either side of a passenger cabin and able to house luggage and/or merchandise, and/or onboard service equipment, and/or removable fuel tanks.

Abstract: Optimization of the use of the available volume in a flying wing for commercial passenger transport, in particular for short- or medium-haul routes. A flying wing is provided including a passenger cabin together with at least one hold for the transport of luggage and/or goods, in which the hold is positioned laterally relative to said passenger cabin.